US7810336B2 - System for introducing fuel to a fluid flow upstream of a combustion area - Google Patents
System for introducing fuel to a fluid flow upstream of a combustion area Download PDFInfo
- Publication number
- US7810336B2 US7810336B2 US11/145,440 US14544005A US7810336B2 US 7810336 B2 US7810336 B2 US 7810336B2 US 14544005 A US14544005 A US 14544005A US 7810336 B2 US7810336 B2 US 7810336B2
- Authority
- US
- United States
- Prior art keywords
- boundary layer
- fuel
- airflow
- downstream
- flow
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related, expires
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/127—Vortex generators, turbulators, or the like, for mixing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/303—Temperature
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2209/00—Safety arrangements
- F23D2209/10—Flame flashback
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2209/00—Safety arrangements
- F23D2209/20—Flame lift-off / stability
Definitions
- the invention relates in general to combustion systems and, more specifically, to systems and methods for delivering fuel to a fluid flow in a combustion system.
- fuel can be mixed with another fluid, such as air, prior to being delivered to and burned in a combustion area.
- another fluid such as air
- FIG. 1 One known system 10 for introducing fuel to an air flow in a turbine engine is shown in FIG. 1 .
- Air 12 from the compressor flows along a surface 14 of a turbine engine combustor component 16 .
- a portion or layer of the air 12 that is at and in the immediate vicinity of the surface 14 is referred to as the boundary layer 18 .
- the air flow 12 has an associated velocity profile 20 .
- the velocity of the air 12 at the boundary layer 18 approaches substantially zero.
- fuel 22 can be introduced to the air flow 12 at or near the boundary layer 18 by a fuel injector 24 .
- Downstream of the fuel injector 24 is a combustion area 26 , which can be, for instance, a transition duct.
- a combustion area 26 Downstream of the fuel injector 24 is a combustion area 26 , which can be, for instance, a transition duct.
- concentrations of the fuel 22 remain on the boundary layer 18 of air 12 , and such fuel 22 moves at relatively low velocities. Consequently, there is an increased risk that flames from the combustion area 26 will be able to travel upstream through such low velocity fuel 22 . If it travels far enough upstream, the flame can be held at the fuel injector 24 due to the continuing supply of fuel 22 , which can result in significant and expensive damage to the injector 24 and the component 16 .
- FIG. 2 One such system 30 is shown in FIG. 2 .
- a fuel injector 24 projects into the flow path 12 and beyond the boundary layer 18 .
- the fuel 22 does not remain on the boundary layer 18 .
- FIG. 3 An example of such a system in a turbine engine is shown in FIG. 3 .
- the combustor section 32 of a turbine engine can include a head end 34 .
- fuel can be injected into the air flow 12 by a fuel ring 36 , which is sometimes referred to as the C-stage.
- the fuel ring 36 is positioned within the air flow path 12 and away from the boundary layer.
- the fuel injectors 24 and/or the fuel ring 36 can fail due to excitations, such as flow induced vibration, combustion dynamics, etc.
- placement of the fuel injectors 24 and/or the fuel ring 36 in the flow path 12 can interfere with the aerodynamics of the flow 12 and can cause a drop in the pressure of the air flow 12 .
- the system includes one or more components that define a surface.
- the one or more components can be, for example, turbine engine combustor components.
- An airflow passes along the surface, and the airflow includes a boundary layer.
- One or more fuel nozzles are disposed within the component and are positioned to inject fuel into the airflow substantially at the boundary layer.
- the fuel nozzle can have an outlet end. In one embodiment, the outlet end can be substantially flush with the surface; thus, the fuel nozzle can be located substantially outside of the airflow.
- a combustion area receives the fuel and airflow.
- the system further includes a turbulence generator positioned at least partially within the boundary layer.
- the turbulence generator is located downstream of the fuel nozzle.
- the turbulence generator causes disturbances in the boundary layer.
- the turbulence generator can be a protrusion extending from the surface and into at least a portion of the boundary layer.
- One or more passages can extend through the protrusion. In such case, a portion of the airflow in the boundary layer can flow through the one or more passages. At least one of the passages can be angled relative to the surface.
- the turbulence generator can be a cross-flow of a fluid into the boundary layer.
- the fluid can be, for example, high pressure air.
- the fluid can be introduced at about 90 degrees relative to the surface.
- the cross-flow can be introduced by a fluid nozzle with an outlet end.
- the fluid nozzle can be disposed within the component such that the outlet end is substantially flush with the surface.
- the fluid nozzle can be located substantially outside of the airflow.
- the turbulence generator can be a combination of a cross-flow of a fluid in the boundary layer and a protrusion extending from the surface and into at least a portion of the boundary layer.
- the system can further include one or more sensors attached to the surface proximate the turbulence generator.
- the one or more sensors can be responsive to temperature changes. Thus, the sensor can alert an operator of temperature increases near the turbulence generator, which can indicate flashback or flame holding.
- the sensor can be a thermocouple.
- the one or more sensors can be located substantially adjacently downstream of the turbulence generator.
- aspects of the invention are directed to a method of introducing fuel to a fluid flow upstream of a combustion area.
- the method involves passing a fluid flow along a surface.
- the fluid flow includes a boundary layer.
- a fuel is injected substantially at the boundary layer.
- the boundary layer is disturbed downstream of the where the fuel is injected and upstream of a combustion area.
- the step of disturbing can be performed by providing one or more protrusions on the surface. Such protrusions can extend into the boundary layer.
- the step of disturbing can be performed by introducing a cross-flow of fluid in at least the boundary layer.
- FIG. 1 is a side elevational view of a prior fuel injection system.
- FIG. 2 is a side elevational view of a second prior fuel injection system.
- FIG. 3 is a side elevational view of a third prior fuel injection system.
- FIG. 4 is a side elevational view of a fuel injection system according to aspects of the invention, wherein boundary layer disturbance is achieved by a protrusion.
- FIG. 5 is a side elevational view of an alternative fuel injection system according to aspects of the invention, wherein boundary layer disturbance is achieved by at least two rows of protrusions.
- FIG. 6 is a side elevational view of another alternative fuel injection system according to aspects of the invention, wherein boundary layer disturbance is achieved by a fluid cross-flow.
- FIG. 7 is a side elevational view of still another alternative fuel injection system according to aspects of the invention, wherein boundary layer disturbance is achieved by a combination of a protrusion and a fluid cross-flow.
- Embodiments of the present invention are directed to fuel introduction systems. Various embodiments of the invention will be explained, but the detailed description is intended only as exemplary. Embodiments of the invention are shown in FIGS. 4-7 , but the present invention is not limited to the illustrated structure or application.
- the fluid can be air 42 , which can be from the compressor section of the turbine engine.
- the portion of air flow 42 that is substantially at and proximate to the surface can be referred to as the boundary layer 48 .
- the air flow 42 has an associated velocity profile 50 . Regardless of the overall velocity profile 50 , the velocity of the air flow 42 in the boundary layer 48 is low, approaching substantially zero at the surface 44 .
- the flow 42 in the boundary layer 48 can be laminar or otherwise substantially non-turbulent.
- fuel 54 can be supplied to the flow 42 in various ways, such as by one or more fuel injectors 52 , nozzles or other fuel delivery device. It should be noted that the fuel 54 can be in various states, such as in gas or liquid form.
- the fuel injectors 52 can have an outlet end 53 through which the fuel 54 exits the injector 52 .
- the outlet end 53 of the fuel injector 52 is substantially flush with the surface 44 .
- the phrase “substantially flush” is intended to mean exactly flush as well as the outlet end 53 of the fuel injector 52 extending slightly beyond or being slightly recessed from the surface 44 .
- the fuel 54 can exit the fuel injector 52 in or near the boundary layer 48 .
- the fuel injectors 52 can be kept substantially outside of the air flow 42 , thereby reducing the exposure of the fuel injectors 52 to operational excitations and potentially averting a pressure drop in the flow 42 .
- the component can be adapted as necessary to accommodate the fuel injectors 52 .
- the fuel injector 52 can be oriented in various ways relative to the surface 44 .
- the fuel injector 52 can be oriented substantially normal to the surface 44 .
- the injectors 52 can be substantially equally or non-equally spaced from each other.
- one or more of the injectors 52 can be offset from the other injectors 52 , such as in the direction of the flow A.
- a combustion area 56 is located downstream of the fuel injectors 52 .
- the path of the flow 42 from the fuel injectors 52 to the combustion area 56 can be substantially straight, or it can include at least one bend, turn or curve.
- the system 40 can be configured to cause a disturbance of the boundary layer 48 downstream of the fuel injector 52 .
- the system can include a turbulence generator provided at least partially within the boundary layer 48 .
- the turbulence generator is located as far downstream from the fuel injectors 52 as possible.
- the turbulence generator can be any of a number of disturbance causing devices, systems, and/or arrangements.
- the turbulence generator can be a contour of the surface 44 .
- the surface contour can be a protrusion 58 extending from the surface 44 .
- the protrusion 58 can have any cross-sectional shape.
- the protrusion 58 can be substantially semi-circular or substantially triangular in conformation, but other shapes are possible.
- the protrusion 58 can extend along the surface 44 and is preferably substantially transverse to the direction of flow A.
- the size of the protrusion 58 including the distance that it projects from the surface 44 can be a function of the velocity of the flow 42 and the quantity of fuel 54 involved, among other things.
- the protrusion 58 can extend substantially continuously along the surface 44 .
- the protrusion 58 can have one or more passages 60 extending therethrough. Ideally, these passages 60 are substantially parallel to the surface 44 . A portion of the air 42 in the boundary layer can flow through the passages 60 , thereby increasing the velocity of the air 42 in the boundary layer 48 .
- the passages 60 can be angled relative to the surface 44 to cause turbulence 62 , such as swirls, within the boundary layer 48 .
- the passages 60 can have a substantially constant cross-sectional area. In one embodiment, there can be reductions in the cross-sectional area of the passages 60 . In the case of two or more passages 60 , the passages 60 can be substantially identical, or at least one of the passages 60 can be different from the other passages 60 in one or more respects.
- the protrusion 58 can be defined by two or more discrete protrusion segments (not shown).
- the two or more protrusion segments can be substantially aligned in a row along the surface 44 .
- the protrusion segments can be in abutting relation.
- At least one protrusion segment can be offset from the other segments, such as in the direction of the flow A. While it is preferred if the individual protrusion segments are substantially identical to each other, at least one of the protrusion segments can be different in any of a number of respects.
- protrusion 58 There can be one or more rows of protrusions 58 .
- the protrusion 58 defining one row may or may not be substantially identical to the protrusion 58 ′ defining another row.
- the protrusions 58 can be provided on the surface 44 in many ways.
- the protrusions 58 can be secured by welding, fasteners (such as pins, bolts or stakes) and/or adhesives, just to name a few possibilities.
- fasteners such as pins, bolts or stakes
- adhesives just to name a few possibilities.
- the fasteners it is preferred if the fasteners can accommodate thermal growth of the protrusion 58 and/or component.
- the protrusions 58 can be unitary with the surface 44 , such as by casting or machining.
- the turbulence generator is not limited to being a protrusion 58 or any other surface feature.
- the turbulence generator can be a fluid cross flow 72 that causes disturbances 62 in the boundary layer 48 . That is, a fluid can be injected into at least the boundary layer 48 so as to create turbulence 62 in the boundary layer 48 . Injection of the fluid can be substantially continuous, or it can be at intervals, regular or irregular or otherwise as needed. Such fluid can be introduced downstream of the fuel injector 52 , preferably as far downstream as possible.
- the fluid 72 can be high pressure air. The air can be taken from a bypass location in the turbine engine, or the air can be taken from an independent source.
- Air is only one example of a suitable fluid that can be used according to aspects of the invention. Aspects of the invention are not limited to any particular fluid 72 , and the fluid 72 can be in gas or liquid form. Ideally, the fluid 72 is selected so that that it will not substantially impede or otherwise interfere with the combustion process. It is also preferred if the fluid 72 is at a sufficient temperature so as not to detract from the combustion process. Further, the fluid 72 is preferably selected so as to have a minimal, if any, effect on the production of exhaust pollutants.
- the fluid 72 can be delivered by one or more injectors 74 , nozzles and/or other fluid delivery devices.
- injectors 74 can be any number of injectors 74 , and the injectors 74 can be arranged in any of a number of ways including at least those discussed above in connection with the fuel injectors 52 .
- the injectors 74 can include an outlet end 75 .
- the outlet ends 75 of the injectors 74 are substantially flush with the surface 44 . Because the fluid injectors 74 are substantially outside of the path of the air flow 42 , the likelihood of excitation-related failure of the injectors 74 can be reduced. Further, by keeping the injectors 74 out of the air flow 42 , the injectors 74 will not significantly contribute to a pressure drop in the air flow 42 .
- the above described cross-flow is yet another manner of achieving a disturbance in the boundary layer 48 of the flow 42 .
- the turbulence generator according to aspects of the invention can further include a combination of a surface contour and a fluid cross-flow.
- both a protrusion 58 and a fluid injector 74 can be provided downstream of the fuel injectors 52 .
- FIG. 7 shows the protrusion 58 located upstream of the fluid injector 74
- aspects of the invention include the opposite arrangement in which the protrusion 58 is located downstream of the fluid injector 74 .
- the turbulence generator according to aspects of the invention can encompass almost any system or structure that can disturb the boundary layer 48 downstream of the fuel injector 52 , and aspects of the invention are not limited to the specific manners described herein.
- the turbulence generator only affects the boundary layer 48 of the flow 42 .
- any disturbances 62 caused by the turbulence generator can occur substantially entirely within the boundary layer 48 of the flow 42 ; that is, there is minimal or no disturbance in the flow 42 outside of the boundary layer 48 .
- the turbulence generator can be completely within the boundary layer 48 . While the turbulence generator can extend beyond the boundary layer 48 , it is preferred if the turbulence generator does not extend substantially beyond the boundary layer 48 .
- Fuel 54 can be introduced to the air flow 42 by the fuel injectors 52 . As the fuel 54 travels downstream, concentrations of the fuel 54 can remain engaged with the boundary layer 48 . When it encounters the turbulence generator, the boundary layer 48 can be disrupted so that turbulence 62 can be created downstream of the turbulence generator. As a result of such disturbances in the boundary layer 48 , the velocity of the fuel 54 that was previously in substantial engagement with the boundary layer 48 can increase. Further, the turbulence 62 can also promote mixing of the fuel 54 and air 42 .
- the disturbance in the boundary layer 48 can be further increased by providing passages 60 in the protrusion 58 , as discussed previously. Air 42 passing though the passages 60 can cause additional disruptions in the downstream air flow. In some instances, the velocity of some vector components of the flow can increase as a result of the air 42 passing through the passages 60 .
- the fuel 54 and air 42 can enter and be ignited in the combustion area 56 , which can include flames.
- flames can be substantially impeded from traveling upstream toward the fuel injector 52 because of the increased velocity of fuel at the boundary layer 48 .
- aspects of the invention can reduce the likelihood that the flame will reach the fuel injector 52 .
- the invention can minimize flame sustainability.
- the fuel injectors 52 can be substantially located outside of the flow path, thereby minimizing concerns of failure of the injectors 52 due to various operational excitations.
- aspects of the invention can further include sensors to detect flashback at or near the location of the boundary layer disturbance.
- the sensors are located substantially proximately downstream of the protrusion 58 or fluid cross-flow 72 .
- the sensors can be thermocouples 80 .
- the thermocouples 80 can be operatively connected to a detection circuit 82 , which can be external to the engine.
- the thermocouple 80 can be responsive to the increased heat produced by flashback or flame holding, thereby alerting an operator of such events. To avoid damage, the operator can change operating conditions, such as reducing engine load, or the operator can shut down the engine.
- aspects of the invention can be applied to known turbine engine combustors.
- the fuel ring 36 and any associated hardware 37 can be removed from the path of the air flow 12 and integrated into the surrounding shell 38 in any of the manners discussed above.
- the absence of the fuel ring 36 in the flow path can have numerous benefits including: avoidance of potential excitation; robustness to excitations; and smaller pressure drops in the flow path.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
Description
Claims (16)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/145,440 US7810336B2 (en) | 2005-06-03 | 2005-06-03 | System for introducing fuel to a fluid flow upstream of a combustion area |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/145,440 US7810336B2 (en) | 2005-06-03 | 2005-06-03 | System for introducing fuel to a fluid flow upstream of a combustion area |
Publications (2)
Publication Number | Publication Date |
---|---|
US20060272332A1 US20060272332A1 (en) | 2006-12-07 |
US7810336B2 true US7810336B2 (en) | 2010-10-12 |
Family
ID=37492766
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/145,440 Expired - Fee Related US7810336B2 (en) | 2005-06-03 | 2005-06-03 | System for introducing fuel to a fluid flow upstream of a combustion area |
Country Status (1)
Country | Link |
---|---|
US (1) | US7810336B2 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140123670A1 (en) * | 2009-01-15 | 2014-05-08 | Alstom Technology Ltd | Gas turbine burner |
US9267689B2 (en) | 2013-03-04 | 2016-02-23 | Siemens Aktiengesellschaft | Combustor apparatus in a gas turbine engine |
US9322558B2 (en) | 2013-06-27 | 2016-04-26 | Siemens Aktiengesellschaft | Combustor apparatus in a gas turbine engine |
US9353949B2 (en) | 2012-04-17 | 2016-05-31 | Siemens Energy, Inc. | Device for improved air and fuel distribution to a combustor |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8689559B2 (en) * | 2009-03-30 | 2014-04-08 | General Electric Company | Secondary combustion system for reducing the level of emissions generated by a turbomachine |
US8260523B2 (en) * | 2009-05-04 | 2012-09-04 | General Electric Company | Method for detecting gas turbine engine flashback |
US10290381B2 (en) * | 2011-12-30 | 2019-05-14 | Ge-Hitachi Nuclear Energy Americas Llc | Method and apparatus for a high-temperature deposition solution injector |
US9761336B2 (en) | 2012-12-20 | 2017-09-12 | Ge-Hitachi Nuclear Energy Americas Llc | Insulated solution injector, system including the same, and method of injecting using the same |
US10036551B2 (en) * | 2014-03-24 | 2018-07-31 | Air Products And Chemicals, Inc. | Low-firing rate oxy-fuel flat flame burner with oxygen staging |
US10515729B2 (en) | 2015-11-04 | 2019-12-24 | Ge-Hitachi Nuclear Energy Americas Llc | Insulated solution injector including an insulating liner, system including the same, and method of injecting using the same |
Citations (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2607191A (en) * | 1947-11-28 | 1952-08-19 | United Aircraft Corp | Vortex producing mechanism for mixing combustion chamber fluids |
US3360929A (en) * | 1966-03-10 | 1968-01-02 | Montrose K. Drewry | Gas turbine combustors |
US3474970A (en) | 1967-03-15 | 1969-10-28 | Parker Hannifin Corp | Air assist nozzle |
US3530667A (en) | 1967-11-02 | 1970-09-29 | Rolls Royce | Fuel injector for gas turbine engines |
US3578264A (en) | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
US4030875A (en) * | 1975-12-22 | 1977-06-21 | General Electric Company | Integrated ceramic-metal combustor |
US4898001A (en) * | 1984-07-10 | 1990-02-06 | Hitachi, Ltd. | Gas turbine combustor |
US5165241A (en) * | 1991-02-22 | 1992-11-24 | General Electric Company | Air fuel mixer for gas turbine combustor |
US5460002A (en) | 1993-05-21 | 1995-10-24 | General Electric Company | Catalytically-and aerodynamically-assisted liner for gas turbine combustors |
US5479781A (en) | 1993-09-02 | 1996-01-02 | General Electric Company | Low emission combustor having tangential lean direct injection |
US5497611A (en) * | 1994-02-18 | 1996-03-12 | Abb Management Ab | Process for the cooling of an auto-ignition combustion chamber |
US5609030A (en) * | 1994-12-24 | 1997-03-11 | Abb Management Ag | Combustion chamber with temperature graduated combustion flow |
US5647215A (en) | 1995-11-07 | 1997-07-15 | Westinghouse Electric Corporation | Gas turbine combustor with turbulence enhanced mixing fuel injectors |
US5676712A (en) * | 1995-05-16 | 1997-10-14 | Atmi Ecosys Corporation | Flashback protection apparatus and method for suppressing deflagration in combustion-susceptible gas flows |
US5941075A (en) | 1996-09-05 | 1999-08-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Fuel injection system with improved air/fuel homogenization |
US6098407A (en) | 1998-06-08 | 2000-08-08 | United Technologies Corporation | Premixing fuel injector with improved secondary fuel-air injection |
US6232005B1 (en) | 1997-11-20 | 2001-05-15 | General Motors Corporation | Fuel cell system combustor |
US6269646B1 (en) | 1998-01-28 | 2001-08-07 | General Electric Company | Combustors with improved dynamics |
US20020069645A1 (en) * | 1999-02-26 | 2002-06-13 | Mowill R. Jan | Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities |
US20030115884A1 (en) | 2001-12-20 | 2003-06-26 | Boardman Gregory A. | Fuel nozzle for a gas turbine engine |
US6598781B2 (en) | 1999-05-03 | 2003-07-29 | General Electric Company | Article having turbulation and method of providing turbulation on an article |
US6681578B1 (en) | 2002-11-22 | 2004-01-27 | General Electric Company | Combustor liner with ring turbulators and related method |
US20040079086A1 (en) | 2002-10-24 | 2004-04-29 | Rolls-Royce, Plc | Piloted airblast lean direct fuel injector with modified air splitter |
US20040079082A1 (en) | 2002-10-24 | 2004-04-29 | Bunker Ronald Scott | Combustor liner with inverted turbulators |
US20040144098A1 (en) | 2000-02-24 | 2004-07-29 | Willis Jeffrey W. | Multi-stage multi-plane combustion method for a gas turbine engine |
-
2005
- 2005-06-03 US US11/145,440 patent/US7810336B2/en not_active Expired - Fee Related
Patent Citations (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2607191A (en) * | 1947-11-28 | 1952-08-19 | United Aircraft Corp | Vortex producing mechanism for mixing combustion chamber fluids |
US3360929A (en) * | 1966-03-10 | 1968-01-02 | Montrose K. Drewry | Gas turbine combustors |
US3474970A (en) | 1967-03-15 | 1969-10-28 | Parker Hannifin Corp | Air assist nozzle |
US3530667A (en) | 1967-11-02 | 1970-09-29 | Rolls Royce | Fuel injector for gas turbine engines |
US3578264A (en) | 1968-07-09 | 1971-05-11 | Battelle Development Corp | Boundary layer control of flow separation and heat exchange |
US3578264B1 (en) | 1968-07-09 | 1991-11-19 | Univ Michigan | |
US4030875A (en) * | 1975-12-22 | 1977-06-21 | General Electric Company | Integrated ceramic-metal combustor |
US4898001A (en) * | 1984-07-10 | 1990-02-06 | Hitachi, Ltd. | Gas turbine combustor |
US5165241A (en) * | 1991-02-22 | 1992-11-24 | General Electric Company | Air fuel mixer for gas turbine combustor |
US5460002A (en) | 1993-05-21 | 1995-10-24 | General Electric Company | Catalytically-and aerodynamically-assisted liner for gas turbine combustors |
US5479781A (en) | 1993-09-02 | 1996-01-02 | General Electric Company | Low emission combustor having tangential lean direct injection |
US5497611A (en) * | 1994-02-18 | 1996-03-12 | Abb Management Ab | Process for the cooling of an auto-ignition combustion chamber |
US5609030A (en) * | 1994-12-24 | 1997-03-11 | Abb Management Ag | Combustion chamber with temperature graduated combustion flow |
US5676712A (en) * | 1995-05-16 | 1997-10-14 | Atmi Ecosys Corporation | Flashback protection apparatus and method for suppressing deflagration in combustion-susceptible gas flows |
US5647215A (en) | 1995-11-07 | 1997-07-15 | Westinghouse Electric Corporation | Gas turbine combustor with turbulence enhanced mixing fuel injectors |
US5941075A (en) | 1996-09-05 | 1999-08-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Fuel injection system with improved air/fuel homogenization |
US6232005B1 (en) | 1997-11-20 | 2001-05-15 | General Motors Corporation | Fuel cell system combustor |
US6269646B1 (en) | 1998-01-28 | 2001-08-07 | General Electric Company | Combustors with improved dynamics |
US6098407A (en) | 1998-06-08 | 2000-08-08 | United Technologies Corporation | Premixing fuel injector with improved secondary fuel-air injection |
US20020069645A1 (en) * | 1999-02-26 | 2002-06-13 | Mowill R. Jan | Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities |
US6598781B2 (en) | 1999-05-03 | 2003-07-29 | General Electric Company | Article having turbulation and method of providing turbulation on an article |
US20040144098A1 (en) | 2000-02-24 | 2004-07-29 | Willis Jeffrey W. | Multi-stage multi-plane combustion method for a gas turbine engine |
US20030115884A1 (en) | 2001-12-20 | 2003-06-26 | Boardman Gregory A. | Fuel nozzle for a gas turbine engine |
US20040079086A1 (en) | 2002-10-24 | 2004-04-29 | Rolls-Royce, Plc | Piloted airblast lean direct fuel injector with modified air splitter |
US20040079082A1 (en) | 2002-10-24 | 2004-04-29 | Bunker Ronald Scott | Combustor liner with inverted turbulators |
US6681578B1 (en) | 2002-11-22 | 2004-01-27 | General Electric Company | Combustor liner with ring turbulators and related method |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140123670A1 (en) * | 2009-01-15 | 2014-05-08 | Alstom Technology Ltd | Gas turbine burner |
US9518743B2 (en) * | 2009-01-15 | 2016-12-13 | General Electric Technology Gmbh | Method for operating a gas turbine burner with a swirl generator |
US9353949B2 (en) | 2012-04-17 | 2016-05-31 | Siemens Energy, Inc. | Device for improved air and fuel distribution to a combustor |
US9267689B2 (en) | 2013-03-04 | 2016-02-23 | Siemens Aktiengesellschaft | Combustor apparatus in a gas turbine engine |
US9322558B2 (en) | 2013-06-27 | 2016-04-26 | Siemens Aktiengesellschaft | Combustor apparatus in a gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
US20060272332A1 (en) | 2006-12-07 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7810336B2 (en) | System for introducing fuel to a fluid flow upstream of a combustion area | |
US8549859B2 (en) | Combustor apparatus in a gas turbine engine | |
US8607575B2 (en) | Method and apparatus for actively controlling fuel flow to a mixer assembly of a gas turbine engine combustor | |
US7942005B2 (en) | Combustion chamber in a turbomachine | |
US9810433B2 (en) | Inclined fuel injection of fuel into a swirler slot | |
US20100071377A1 (en) | Combustor Apparatus for Use in a Gas Turbine Engine | |
US9267687B2 (en) | Combustion system having a venturi for reducing wakes in an airflow | |
CN106524224B (en) | System and method with annular flow path architecture | |
CN103672965A (en) | Gas turbine combustor | |
US9416973B2 (en) | Micromixer assembly for a turbine system and method of distributing an air-fuel mixture to a combustor chamber | |
CN101675227A (en) | Cooling structure for gas-turbine combustor | |
US20150075172A1 (en) | Flamesheet combustor contoured liner | |
GB2451144A (en) | Method and apparatus for actively controlling fuel flow to a mixer assembly of a gas turbine engine combustor | |
EP1801503A2 (en) | Combustor nozzle | |
US8186165B2 (en) | Turbine fuel nozzle having heat control | |
US9360218B2 (en) | Injection device for a combustion chamber of a turbine engine | |
US10871075B2 (en) | Cooling passages in a turbine component | |
US8291705B2 (en) | Ultra low injection angle fuel holes in a combustor fuel nozzle | |
RU2533609C2 (en) | Burner flame stabilisation | |
Schildmacher et al. | Unsteady flame and flow field interaction of a premixed model gas turbine burner | |
CA2595061C (en) | Method and apparatus for actively controlling fuel flow to a mixer assembly of a gas turbine engine combustor | |
JP2014517250A (en) | Method for injecting fuel into a combustion chamber of a gas turbine and injection system for implementing the same | |
EP3221643B1 (en) | Combustion liner and method of reducing a recirculation zone of a combustion liner | |
US20160320062A1 (en) | Nozzle for a gas turbine combustor | |
JP4995657B2 (en) | Apparatus for actively controlling fuel flow to a gas turbine engine combustor mixer assembly |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: SIEMENS WESTINGHOUSE POWER CORPORATION, FLORIDA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:MORAES, RICARDO F.;REEL/FRAME:016665/0223 Effective date: 20050527 |
|
AS | Assignment |
Owner name: SIEMENS POWER GENERATION, INC.,FLORIDA Free format text: CHANGE OF NAME;ASSIGNOR:SIEMENS WESTINGHOUSE POWER CORPORATION;REEL/FRAME:017000/0120 Effective date: 20050801 Owner name: SIEMENS POWER GENERATION, INC., FLORIDA Free format text: CHANGE OF NAME;ASSIGNOR:SIEMENS WESTINGHOUSE POWER CORPORATION;REEL/FRAME:017000/0120 Effective date: 20050801 |
|
AS | Assignment |
Owner name: SIEMENS ENERGY, INC., FLORIDA Free format text: CHANGE OF NAME;ASSIGNOR:SIEMENS POWER GENERATION, INC.;REEL/FRAME:022488/0630 Effective date: 20081001 Owner name: SIEMENS ENERGY, INC.,FLORIDA Free format text: CHANGE OF NAME;ASSIGNOR:SIEMENS POWER GENERATION, INC.;REEL/FRAME:022488/0630 Effective date: 20081001 |
|
FPAY | Fee payment |
Year of fee payment: 4 |
|
FEPP | Fee payment procedure |
Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.) |
|
LAPS | Lapse for failure to pay maintenance fees |
Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20181012 |